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US8647073B2 - Abrasive single-crystal turbine blade - Google Patents

Abrasive single-crystal turbine blade Download PDF

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Publication number
US8647073B2
US8647073B2 US12/917,071 US91707110A US8647073B2 US 8647073 B2 US8647073 B2 US 8647073B2 US 91707110 A US91707110 A US 91707110A US 8647073 B2 US8647073 B2 US 8647073B2
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Prior art keywords
resistant
oxidation
coating
turbine blade
weight
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US20110103967A1 (en
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Matthias Hoebel
Alexander Schnell
Yves PELLATON
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Ansaldo Energia IP UK Ltd
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Alstom Technology AG
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/34—Laser welding for purposes other than joining
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
    • B23K35/24—Selection of soldering or welding materials proper
    • B23K35/30—Selection of soldering or welding materials proper with the principal constituent melting at less than 1550 degrees C
    • B23K35/3033—Ni as the principal constituent
    • B23K35/304—Ni as the principal constituent with Cr as the next major constituent
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
    • B23K35/24—Selection of soldering or welding materials proper
    • B23K35/32—Selection of soldering or welding materials proper with the principal constituent melting at more than 1550 degrees C
    • B23K35/327—Selection of soldering or welding materials proper with the principal constituent melting at more than 1550 degrees C comprising refractory compounds, e.g. carbides
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C26/00—Coating not provided for in groups C23C2/00 - C23C24/00
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/347—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with layers adapted for cutting tools or wear applications
    • C—CHEMISTRY; METALLURGY
    • C30—CRYSTAL GROWTH
    • C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
    • C30B13/00—Single-crystal growth by zone-melting; Refining by zone-melting
    • C30B13/16—Heating of the molten zone
    • C30B13/22—Heating of the molten zone by irradiation or electric discharge
    • C30B13/24—Heating of the molten zone by irradiation or electric discharge using electromagnetic waves
    • C—CHEMISTRY; METALLURGY
    • C30—CRYSTAL GROWTH
    • C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
    • C30B29/00—Single crystals or homogeneous polycrystalline material with defined structure characterised by the material or by their shape
    • C30B29/10—Inorganic compounds or compositions
    • C30B29/52—Alloys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/001—Turbines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/34—Coated articles, e.g. plated or painted; Surface treated articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/08—Non-ferrous metals or alloys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition

Definitions

  • the invention deals with the field of gas turbine engineering and materials science. It relates to an abrasive single-crystal turbine blade having a high resistance to oxidation and frictional wear and also to a method for producing such an abrasive single-crystal turbine blade.
  • EP 1295969 A1 and EP 1295970 A1 disclose MCrAlY materials which are used as coatings which protect against oxidation, have a relatively large surface area and have the best possible adaptation to a single-crystal basic material.
  • the (epitaxial) E-LMF method is also likewise known for the controlled remelting of or metal forming on single-crystal components (EP 1476272 B1).
  • the disclosure is directed to a turbine blade for a turbine rotor.
  • the blade has a single-crystal basic body including a blade tip and extends in the radial direction.
  • At least one oxidation-resistant intermediate coating which is applied by laser metal forming and is epitaxially bonded to the basic body, is arranged on a radially outer blade tip.
  • An at least single-layer, wear-resistant and oxidation-resistant coating which is applied by laser metal forming and includes an oxidation-resistant binder material and abrasive particles embedded therein, is arranged on at least portions of the epitaxial intermediate coating.
  • the disclosure is directed to a method for producing a turbine blade for a turbine rotor.
  • the blade has a single-crystal basic body including a blade tip and extends in the radial direction.
  • At least one oxidation-resistant intermediate coating which is applied by laser metal forming and is epitaxially bonded to the basic body, is arranged on a radially outer blade tip.
  • the method includes applying, epitaxially, at least one oxidation-resistant intermediate coating, by laser metal forming, to the surface of the basic body on the radially outer blade tip.
  • the method also includes applying an at least single-layer, wear-resistant and oxidation-resistant coating, by laser metal forming, to at least portions of the epitaxial intermediate coating.
  • FIGS. 1 to 5 show an exemplary embodiment of the invention. The invention is explained in more detail below on the basis of exemplary embodiments and with reference to FIGS. 1 to 5 , in which:
  • FIG. 1 shows a turbine blade for the rotor of a gas turbine according to a first exemplary embodiment of the invention
  • FIG. 2 shows a schematic section along line II-II in FIG. 1 ;
  • FIGS. 3 a , 3 b , and 3 c show the production sequence for the production of an abrasive single-crystal turbine blade according to a second exemplary embodiment of the invention
  • FIG. 4 shows photographic images of a combination of coatings, produced by the LMF method, on a single-crystal turbine blade
  • FIG. 5 shows the coating apparatus and the principle of the E-LMF method.
  • the aim of the invention is to avoid the disadvantages of the known prior art.
  • the invention is based on the object of developing an abrasive single-crystal turbine blade which is distinguished by a high resistance to oxidation and frictional wear, where particular attention is paid to the demands made on the process, which arise owing to the single-crystal nature of the blade material.
  • the invention deals with the application for reconditioning or retrofitting single-crystal components.
  • this object is achieved in that the following features are implemented in a turbine blade for the rotor of a turbine, having a single-crystal basic body which has a blade tip and extends in the radial direction r (in relation to the rotor):
  • At least one oxidation-resistant intermediate coating is epitaxially applied by laser metal forming to the surface of the basic body on the radially outer blade tip, and an at least single-layer, wear-resistant and oxidation-resistant coating consisting of oxidation-resistant binder material and abrasive particles embedded therein is applied by laser metal forming to at least certain regions of said epitaxial intermediate coating.
  • the temperature or temperature distribution in the melt pool is advantageously recorded online during the build-up of the intermediate coating and of the wear-resistant and oxidation-resistant coating by the laser metal forming method, such that this information can be used, with the aid of a control system, to control the laser power during the laser metal forming method and/or the relative movement between the laser beam and the turbine blade such that the quotient G n /V s lies above the material-dependent limit value required for directional, single-crystal solidification, where G denotes the local temperature gradient, V s denotes the speed of the solidification front and n denotes a further material parameter.
  • the advantages of the invention are that single-crystal turbine blades are realized with an optimized service life of the abrasive blade tip at high operating temperatures. Together with a suitable grazing coating on the stator side, the leakage losses via the hot gas breach are reduced and the efficiency of the turbine is increased.
  • the oxidation-resistant intermediate coating and the radially outer abrasive coating are generated by laser metal forming.
  • the abrasive blade tip is realized by laser metal forming (LMF). It is preferable to take special demands made on the material and process into account for use on single-crystal turbine blades.
  • LMF laser metal forming
  • an oxidation-resistant, single-crystal buffer coating is initially realized at the interface with the blade body, and this coating solidifies epitaxially on the single-crystal basic body of the turbine blade. The actual abrasive coating is then applied to this epitaxially bonded buffer coating.
  • An essential feature of the abrasive coating is the complete embedding of the abrasive particles in an oxidation-resistant matrix.
  • a further feature is the homogeneous distribution of the abrasive particles in the abrasive coating.
  • an abrasive single-crystal turbine blade can advantageously be used both for producing new parts and for retrofitting with only minimum adaptation of existing production processes.
  • the epitaxial intermediate coating is produced from an oxidation-resistant MCrAlY alloy (in the context of the present disclosure, M stands for Ni, Co or a combination of both elements) of the ⁇ / ⁇ or ⁇ / ⁇ ′ type, the chemical composition of which is selected such that upon epitaxial solidification firstly the ⁇ phase and only then the ⁇ or ⁇ ′ phase is formed.
  • M oxidation-resistant MCrAlY alloy
  • M stands for Ni, Co or a combination of both elements
  • the chemical composition of said alloy is selected such that it lies in the ⁇ phase region and close to the eutectic boundary line between the ⁇ and ⁇ or ⁇ ′ phase regions in the ternary Ni—Al—Cr phase diagram.
  • This also applies to the Ni/Co—Cr—Al phase diagram, since Ni and Co are completely miscible, i.e. Co does not influence the solidification behavior, but only the ⁇ phase stability temperature or the ⁇ phase proportion.
  • the intermediate coating applied epitaxially to the single-crystal basic body consists of an oxidation-resistant superalloy of the ⁇ / ⁇ or ⁇ / ⁇ ′ type having the following chemical composition (amounts in % by weight): 15-30 Cr, 5-10 Al, 0.3-1.2 Y, 0.1-1.2 Si, 0-2 others, remainder Ni, Co, or of an oxidation-resistant superalloy of the ⁇ / ⁇ type having the following chemical composition (amounts in % by weight): 35-39 Co, 18-24 Cr, 7-9 Al, 0.3-0.8 Y, 0.1-1 Si, 0-2 others, remainder Ni, or of an oxidation-resistant superalloy of the ⁇ / ⁇ ′ type having the following chemical composition (amounts in % by weight): 18-26 Cr, 5-8 Al, 0.3-1.2 Y, 0.1-1.2 Si, 0-2 others, remainder Ni, Co.
  • These materials are particularly suitable as intermediate coatings. It is advantageous if the material has a solidification
  • the epitaxial intermediate coating consists of oxidation-resistant material having a chemical composition which is optimized for use with the LMF method.
  • the composition of the material is selected such that, upon solidification from the melt phase, firstly the ⁇ phase is formed and solidifies epitaxially on the basic body of the turbine blade.
  • the material used for the oxidation-resistant intermediate coating is simultaneously also used as binder material in the wear-resistant and oxidation-resistant coating, because this improves the compatibility of the two coatings further, which has a particularly positive effect on their properties.
  • cBN cubic boron nitride
  • FIG. 1 is a perspective illustration of a turbine blade 1 for a rotor 2 (shown schematically) of a gas turbine, while FIG. 2 shows a section along line II-II in FIG. 1 in enlarged form.
  • the turbine blade 1 has a single-crystal basic body 4 , which extends in the radial direction r (in relation to the rotor) and, according to the invention, has an epitaxial, oxidation-resistant intermediate coating 5 , which is applied by LMF and has a wear-resistant and oxidation-resistant coating 6 (see FIG. 2 ) applied thereto, on the blade tip 3 .
  • the coating 6 covers the entire intermediate coating 5 , although it is also possible for it to only partially cover the intermediate coating 5 .
  • the basic material of the basic blade body is, for example, a single-crystal nickel-based superalloy.
  • the surface of the basic body 4 was uncoated before the LMF method was employed.
  • Both coatings 5 and 6 can have a single-layer or else multi-layer form.
  • the length L of the turbine blade 1 can readily be varied by the number of coatings 5 , 6 applied by LMF methods (or by the number of layers applied).
  • the epitaxial intermediate coating 5 is comprised of oxidation-resistant material having a chemical composition which is optimized for use with the LMF method.
  • the composition of the material is selected such that, upon solidification from the melt phase, firstly the ⁇ phase is formed and solidifies epitaxially on the basic body 4 of the turbine blade 1 .
  • the composition of the material is optimized such that the solidification interval between the solidus temperature and liquidus temperature is ⁇ 50 K and preferably ⁇ 30 K.
  • the epitaxial intermediate coating 5 can be applied directly to the blade tip 3 of an uncoated, single-crystal turbine blade 1 .
  • the epitaxial intermediate coating 5 is applied such that it at least partially overlaps with other, existing protective coatings.
  • the existing protective coatings may be, for example, so-called MCrAlY coatings 11 (M ⁇ Ni, Co or a combination of both elements) which, in the case of most turbine blades subject to high levels of loading, protect the surfaces of the main blade section against oxidation and corrosion (see FIG. 3 ).
  • TBC ceramic thermal barrier coating
  • Single-crystal, epitaxial solidification of the oxidation-resistant intermediate coating 5 on the single-crystal basic body 4 of the blade 1 can be achieved by using the material which is specially designed for the LMF process for the binder 7 and the intermediate coating 5 , and also by controlled conduction of the process, preferably with online control of the laser power.
  • the risk of cracking during solidification is minimized by the optimized composition of the material used as the intermediate coating 5 and as the binder 7 .
  • Efficient protection of those surfaces of the blade tip 3 which are exposed to the hot gas is ensured by the overlapping of the oxidation-resistant intermediate coating 5 with further protective coatings 11 , 12 which may be present on the main blade section.
  • oxidation-resistant material can be applied to the first intermediate coating 5 .
  • the actual abrasive coating 6 is applied either directly to the epitaxial intermediate coating 5 or to the topmost layer of oxidation-resistant material.
  • abrasive particles are mixed together with oxidation-resistant binder material (preferably made of the material used for the intermediate coating(s)) and applied by the LMF method.
  • the abrasive coating 6 does not have to completely cover the intermediate coating 5 , but instead can be formed as an individual strip or as a combination of segments of individual strips.
  • the realization of the abrasive, single-crystal blade tip by the E-LMF method after preceding, conventional coating of the main blade section is particularly interesting: in this process sequence, existing production processes have to be modified only minimally and it is possible to dispense with the masking of the abrasive coating during the application of the MCrAlY protective coatings on the main blade section.
  • the component (turbine blade 1 ) can therefore be used without carrying out further, subsequent steps immediately after the abrasive blade tip has been applied. It is advantageously possible to dispense with further heat treatment.
  • FIG. 3 One possible production sequence for the production of an abrasive single-crystal turbine blade 1 according to the invention is shown in FIG. 3 .
  • An MCrAlY adhesive coating 11 is applied to the surface of a blade body 4 , which consists of a single-crystal material, for example a single-crystal Ni-based superalloy, and a ceramic thermal barrier coating (TBC) 12 is applied in turn to said adhesive coating (see FIG. 3 a ).
  • TBC ceramic thermal barrier coating
  • the coating on the radially outer blade tip 3 which is in the form of a crown in this exemplary embodiment, is removed mechanically and/or chemically, e.g. ground away, milled away or etched away (see FIG.
  • an epitaxially solidified intermediate coating 5 and an abrasive coating 6 thereon are then applied by E-LMF (see FIG. 3 c ).
  • FIG. 4 shows photographic images of an exemplary realization of such an abrasive single-crystal blade tip 3 , which was produced by the LMF method.
  • the blade tip 3 is designed as a crown.
  • the radiation source used was a fiber-coupled high-power diode laser having an output power of 1000 W.
  • the intermediate coating 5 (buffer coating), which is solidified epitaxially and in single-crystal form and is comprised of the alloy known commercially under the name Amdry 995, is firstly arranged on the single-crystal basic body 4 (nickel-based superalloy MK4) on the radially outer surface, the optimum microstructure of said coating also continuing at the interface with the overlying abrasive coating 6 which, in this exemplary embodiment, consists of Amdry 995 as binder material 7 and cBN particles embedded therein as abrasive material 8 . Naturally, continuation of the single-crystal microstructure is no longer possible above the first abrasive particles 8 .
  • the following alloys are suitable as the material for the epitaxial intermediate coating 5 or as binder material 7 :
  • these materials are particularly suitable as intermediate coatings 5 , but also as binder material 7 in the abrasive coatings 6 . It is advantageous if the material has a solidification interval between the solidus temperature and liquidus temperature ⁇ T 0 of less than 50 K and preferably less than 30 K. This reduces the risk of cracking during solidification.
  • FIG. 5 shows a coating apparatus 13 for carrying out the method according to the invention and the (epitaxial) LMF process with coaxial injection of the powder particles about a focused, high-intensity laser beam 10 .
  • the apparatus 13 is described in detail in U.S. Pat. No. 7,586,061 (B2), the contents of which are incorporated by reference as if fully set forth. Movement of the powder nozzle (or of the workpiece, here turbine blade 1 ), which is effected with the aid of a robot (not shown), permits full 6-axis flexibility of the process.
  • a dichroic mirror 14 deflects the high-intensity laser light 10 onto the component 1 and focuses it at a small aiming point.
  • the mirror 14 is transparent to the process light, which is coupled to an optical pyrometer (not shown) which makes online control of the temperature of the melt pool 16 possible.
  • the material 7 for the intermediate coating 5 (or abrasive material 8 and oxidation-resistant binder material 7 for the coating 6 ) is (are) mixed in a powder nozzle, transported by a carrier gas 15 and then injected concentrically about the laser beam 10 as a focused jet of powder into the melt pool 16 produced by the laser beam 10 on the blade tip 3 .
  • the temperature or temperature distribution in the melt pool is recorded online during the laser metal forming (optical temperature signal 17 ), and this information is used, with the aid of a control system (not shown), to control the laser power during the laser metal forming and/or to change the relative movement between the laser beam 10 and the turbine blade 1 in a controlled manner.
  • the integrated pyrometer makes it possible to determine the temperature of the melt pool during the laser process.
  • the laser controller (not shown)
  • the quotient G n /V s has to lie above a material-dependent limit value required for directional, single-crystal solidification.
  • G denotes the local temperature gradient
  • V s denotes the speed of the solidification front
  • n denotes a further material parameter.
  • the present disclosure provides an inexpensive and simple method for producing abrasive protective coatings for single-crystal turbine blades.
  • the useful service life of the abrasive coating at high operating temperatures is increased by the complete embedding of the abrasive particles in an oxidation-resistant binder matrix.
  • the advantages of abrasive coatings can thus be ensured at least for the duration of the running-in operation.
  • E-LMF epitaxial laser metal forming
  • the abrasive coatings of single-crystal turbine blades have a very high commercial potential in powerful turbines of the most recent generation.
  • the present invention makes it possible to reduce the leakage between the heat shield and the tips of the turbine blades. Over the useful service life of the abrasive coating, ovalization of the housing or eccentricity between the rotor and the housing as a result of the turbine blades grinding in can be corrected as part of a suitably configured run-in procedure.
  • the increased resistance to wear of the abrasive turbine blade with respect to frictional contacts makes it possible to apply relatively dense ceramic coatings to the heat shields. Good rub-in behavior during a run-in procedure can thus be combined with the requisite long-term erosion resistance of the ceramic coatings on the heat shields.
  • the method can be used with all single-crystal turbine blades 1 .
  • the limited service life of the abrasive coating 6 which is dependent on the respective operating conditions (temperature, fuel), must be taken into consideration.
  • the service life is optimized by good distribution and complete embedding of the abrasive particles 8 in the oxidation-resistant binder matrix 7 . Nevertheless, the main aim is to protect the turbine blade tip 3 above all during the run-in phase (several dozen to several hundred operating hours).
  • a run-in procedure tailored to the abrasive turbine blades 1 should be used.

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Abstract

A turbine blade for a turbine rotor, is provided having a single-crystal basic body which has a blade tip and extends in the radial direction. The turbine blade includes at least one oxidation-resistant intermediate coating, which is applied by laser metal forming and is epitaxially bonded to the basic body, is arranged on the radially outer blade tip, and in that an at least single-layer, wear-resistant and oxidation-resistant coating, which is applied by laser metal forming and consists of oxidation-resistant binder material and abrasive particles embedded therein, is arranged on at least certain regions of said epitaxial intermediate coating.

Description

FIELD OF INVENTION
The invention deals with the field of gas turbine engineering and materials science. It relates to an abrasive single-crystal turbine blade having a high resistance to oxidation and frictional wear and also to a method for producing such an abrasive single-crystal turbine blade.
BACKGROUND
The reduction of leakage losses in turbines has been the subject of intensive development work for several decades. During operation of a gas turbine, relative movement between the rotor and the housing is unavoidable. The resultant wear of the housing or wear of the blades has the effect that a sealing action is no longer provided. As a solution to this problem, a combination of thick coatings which can be ground away on the heat shield and abrasive protective coatings on the blade tips is provided.
Methods for applying additional coatings to blade tips or for increasing the resistance to wear by suitable modification of the blade tip have been known even since the 1970s. Various methods have likewise been proposed for simultaneously making such protective coatings resistant to frictional contacts and oxidation caused by the hot gas by a combination of abrasive particles (carbides, nitrides, etc.) with oxidation-resistant materials. Many of the proposed methods are expensive and complex to implement, however, making commercial use more difficult. This applies above all also to the application of these methods for single-crystal turbine blades. Here, additional demands are made on the production process because of the special single-crystal microstructure of the basic material. In particular, the production of the abrasive blade tip should have the smallest possible influence on the basic body of the turbine blade. This includes the avoidance of defects at the interface with the basic body of the blade.
One of the popular strategies therefore lies in dispensing entirely with the protection of the blade tip against wear and providing the heat shield with special porous, ceramic rub-in coatings. Owing to their high porosity, these can also be rubbed in to a certain extent by unprotected blade tips. However, considerable technical risks are associated with this method, since the porous, ceramic rub-in coatings do not ensure the same resistance to erosion as dense coatings. A further risk lies in operational changes to the porous, ceramic rub-in coatings (densification by sintering), which can have a negative effect on the tribological properties. For this reason, a combination with wear-resistant (abrasive) blade tips is expedient when using ceramic protective coatings on heat shields.
Turbine blades with abrasive coatings have been known since the 1960s. In recent decades, a plurality of methods for producing abrasive blade tips have been developed as shown, for example, in U.S. Pat. No. 6,194,086 B1. Although the use of laser metal forming (LMF) to build up abrasive blade tips has been known since the start of the 1990s (see for example DE 10 2004 059 904 A1), this method is still used rarely on an industrial scale.
EP 1295969 A1 and EP 1295970 A1 disclose MCrAlY materials which are used as coatings which protect against oxidation, have a relatively large surface area and have the best possible adaptation to a single-crystal basic material.
The (epitaxial) E-LMF method is also likewise known for the controlled remelting of or metal forming on single-crystal components (EP 1476272 B1).
However, the production of abrasive protective coatings with an epitaxially solidified intermediate coating on a single-crystal basic material is not yet known.
SUMMARY
The disclosure is directed to a turbine blade for a turbine rotor. The blade has a single-crystal basic body including a blade tip and extends in the radial direction. At least one oxidation-resistant intermediate coating, which is applied by laser metal forming and is epitaxially bonded to the basic body, is arranged on a radially outer blade tip. An at least single-layer, wear-resistant and oxidation-resistant coating, which is applied by laser metal forming and includes an oxidation-resistant binder material and abrasive particles embedded therein, is arranged on at least portions of the epitaxial intermediate coating.
In another aspect, the disclosure is directed to a method for producing a turbine blade for a turbine rotor. The blade has a single-crystal basic body including a blade tip and extends in the radial direction. At least one oxidation-resistant intermediate coating, which is applied by laser metal forming and is epitaxially bonded to the basic body, is arranged on a radially outer blade tip. An at least single-layer, wear-resistant and oxidation-resistant coating, which is applied by laser metal forming and includes an oxidation-resistant binder material and abrasive particles embedded therein, is arranged on at least portions of the epitaxial intermediate coating. The method includes applying, epitaxially, at least one oxidation-resistant intermediate coating, by laser metal forming, to the surface of the basic body on the radially outer blade tip. The method also includes applying an at least single-layer, wear-resistant and oxidation-resistant coating, by laser metal forming, to at least portions of the epitaxial intermediate coating.
BRIEF DESCRIPTION OF THE DRAWINGS
The drawings show an exemplary embodiment of the invention. The invention is explained in more detail below on the basis of exemplary embodiments and with reference to FIGS. 1 to 5, in which:
FIG. 1 shows a turbine blade for the rotor of a gas turbine according to a first exemplary embodiment of the invention;
FIG. 2 shows a schematic section along line II-II in FIG. 1;
FIGS. 3 a, 3 b, and 3 c show the production sequence for the production of an abrasive single-crystal turbine blade according to a second exemplary embodiment of the invention;
FIG. 4 shows photographic images of a combination of coatings, produced by the LMF method, on a single-crystal turbine blade, and
FIG. 5 shows the coating apparatus and the principle of the E-LMF method.
 DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Introduction to the Embodiments
The aim of the invention is to avoid the disadvantages of the known prior art. The invention is based on the object of developing an abrasive single-crystal turbine blade which is distinguished by a high resistance to oxidation and frictional wear, where particular attention is paid to the demands made on the process, which arise owing to the single-crystal nature of the blade material. Similarly, the invention deals with the application for reconditioning or retrofitting single-crystal components.
According to the invention, this object is achieved in that the following features are implemented in a turbine blade for the rotor of a turbine, having a single-crystal basic body which has a blade tip and extends in the radial direction r (in relation to the rotor):
    • at least one oxidation-resistant intermediate coating, which is applied by known laser metal forming and is epitaxially bonded to the basic body, is arranged on the radially outer blade tip, and
    • an at least single-layer, wear-resistant and oxidation-resistant coating, which is applied by laser metal forming and consists of oxidation-resistant binder material and abrasive particles embedded therein, is arranged on at least certain regions of said epitaxial intermediate coating.
In the method according to the invention for producing such a single-crystal turbine blade, at least one oxidation-resistant intermediate coating is epitaxially applied by laser metal forming to the surface of the basic body on the radially outer blade tip, and an at least single-layer, wear-resistant and oxidation-resistant coating consisting of oxidation-resistant binder material and abrasive particles embedded therein is applied by laser metal forming to at least certain regions of said epitaxial intermediate coating. The temperature or temperature distribution in the melt pool is advantageously recorded online during the build-up of the intermediate coating and of the wear-resistant and oxidation-resistant coating by the laser metal forming method, such that this information can be used, with the aid of a control system, to control the laser power during the laser metal forming method and/or the relative movement between the laser beam and the turbine blade such that the quotient Gn/Vs lies above the material-dependent limit value required for directional, single-crystal solidification, where G denotes the local temperature gradient, Vs denotes the speed of the solidification front and n denotes a further material parameter.
The advantages of the invention are that single-crystal turbine blades are realized with an optimized service life of the abrasive blade tip at high operating temperatures. Together with a suitable grazing coating on the stator side, the leakage losses via the hot gas breach are reduced and the efficiency of the turbine is increased.
It is particularly advantageous that the oxidation-resistant intermediate coating and the radially outer abrasive coating are generated by laser metal forming.
The abrasive blade tip is realized by laser metal forming (LMF). It is preferable to take special demands made on the material and process into account for use on single-crystal turbine blades. In this respect, an oxidation-resistant, single-crystal buffer coating is initially realized at the interface with the blade body, and this coating solidifies epitaxially on the single-crystal basic body of the turbine blade. The actual abrasive coating is then applied to this epitaxially bonded buffer coating. An essential feature of the abrasive coating is the complete embedding of the abrasive particles in an oxidation-resistant matrix. A further feature is the homogeneous distribution of the abrasive particles in the abrasive coating.
The described embodiment of an abrasive single-crystal turbine blade can advantageously be used both for producing new parts and for retrofitting with only minimum adaptation of existing production processes.
Further advantageous refinements are described in the dependent claims.
By way of example, the epitaxial intermediate coating is produced from an oxidation-resistant MCrAlY alloy (in the context of the present disclosure, M stands for Ni, Co or a combination of both elements) of the γ/β or γ/γ′ type, the chemical composition of which is selected such that upon epitaxial solidification firstly the γ phase and only then the β or γ′ phase is formed.
It is advantageous if the chemical composition of said alloy is selected such that it lies in the γ phase region and close to the eutectic boundary line between the γ and β or γ′ phase regions in the ternary Ni—Al—Cr phase diagram. This also applies to the Ni/Co—Cr—Al phase diagram, since Ni and Co are completely miscible, i.e. Co does not influence the solidification behavior, but only the β phase stability temperature or the β phase proportion.
Furthermore, it is advantageous if the intermediate coating applied epitaxially to the single-crystal basic body consists of an oxidation-resistant superalloy of the γ/β or γ/γ′ type having the following chemical composition (amounts in % by weight): 15-30 Cr, 5-10 Al, 0.3-1.2 Y, 0.1-1.2 Si, 0-2 others, remainder Ni, Co, or of an oxidation-resistant superalloy of the γ/γ type having the following chemical composition (amounts in % by weight): 35-39 Co, 18-24 Cr, 7-9 Al, 0.3-0.8 Y, 0.1-1 Si, 0-2 others, remainder Ni, or of an oxidation-resistant superalloy of the γ/γ′ type having the following chemical composition (amounts in % by weight): 18-26 Cr, 5-8 Al, 0.3-1.2 Y, 0.1-1.2 Si, 0-2 others, remainder Ni, Co. These materials are particularly suitable as intermediate coatings. It is advantageous if the material has a solidification interval between the solidus temperature and liquidus temperature ΔTo of less than 50 K and preferably less than 30 K. This reduces the risk of cracking during solidification.
The epitaxial intermediate coating consists of oxidation-resistant material having a chemical composition which is optimized for use with the LMF method. The composition of the material is selected such that, upon solidification from the melt phase, firstly the γ phase is formed and solidifies epitaxially on the basic body of the turbine blade.
Furthermore, it is advantageous if the material used for the oxidation-resistant intermediate coating is simultaneously also used as binder material in the wear-resistant and oxidation-resistant coating, because this improves the compatibility of the two coatings further, which has a particularly positive effect on their properties.
Moreover, it has proved to be expedient to use cubic boron nitride (cBN) as the abrasive material in the wear-resistant and oxidation-resistant coating. In the case of multi-layer wear-resistant and oxidation-resistant coatings, it is advantageous if the proportion of abrasive material increases outward in the radial direction r, because then the outermost coating has the highest proportion of abrasive material and thus the highest resistance to wear.
DETAILED DESCRIPTION
FIG. 1 is a perspective illustration of a turbine blade 1 for a rotor 2 (shown schematically) of a gas turbine, while FIG. 2 shows a section along line II-II in FIG. 1 in enlarged form. The turbine blade 1 has a single-crystal basic body 4, which extends in the radial direction r (in relation to the rotor) and, according to the invention, has an epitaxial, oxidation-resistant intermediate coating 5, which is applied by LMF and has a wear-resistant and oxidation-resistant coating 6 (see FIG. 2) applied thereto, on the blade tip 3. Here, the coating 6 covers the entire intermediate coating 5, although it is also possible for it to only partially cover the intermediate coating 5. The basic material of the basic blade body is, for example, a single-crystal nickel-based superalloy. In this first exemplary embodiment, the surface of the basic body 4 was uncoated before the LMF method was employed. Both coatings 5 and 6 can have a single-layer or else multi-layer form. The length L of the turbine blade 1 can readily be varied by the number of coatings 5, 6 applied by LMF methods (or by the number of layers applied).
One concept on which the invention is based is that of building up the abrasive coating 6 on the intermediate coating 5 (buffer coating) which is epitaxially solidified on the single-crystal basic blade body 4. The epitaxial intermediate coating 5 is comprised of oxidation-resistant material having a chemical composition which is optimized for use with the LMF method. The composition of the material is selected such that, upon solidification from the melt phase, firstly the γ phase is formed and solidifies epitaxially on the basic body 4 of the turbine blade 1. In order to reduce the risk of cracking during solidification, the composition of the material is optimized such that the solidification interval between the solidus temperature and liquidus temperature is <50 K and preferably <30 K.
In a first variant (as shown in FIGS. 1 and 2), the epitaxial intermediate coating 5 can be applied directly to the blade tip 3 of an uncoated, single-crystal turbine blade 1. In an alternative approach, the epitaxial intermediate coating 5 is applied such that it at least partially overlaps with other, existing protective coatings. In this case, the existing protective coatings may be, for example, so-called MCrAlY coatings 11 (M═Ni, Co or a combination of both elements) which, in the case of most turbine blades subject to high levels of loading, protect the surfaces of the main blade section against oxidation and corrosion (see FIG. 3). In a further, third variant (see FIG. 3), there is also an additional ceramic thermal barrier coating (TBC) 12 on the main blade section, which is not damaged by the subsequent build-up of the abrasive blade tip.
Single-crystal, epitaxial solidification of the oxidation-resistant intermediate coating 5 on the single-crystal basic body 4 of the blade 1 can be achieved by using the material which is specially designed for the LMF process for the binder 7 and the intermediate coating 5, and also by controlled conduction of the process, preferably with online control of the laser power. The risk of cracking during solidification is minimized by the optimized composition of the material used as the intermediate coating 5 and as the binder 7. Efficient protection of those surfaces of the blade tip 3 which are exposed to the hot gas is ensured by the overlapping of the oxidation-resistant intermediate coating 5 with further protective coatings 11, 12 which may be present on the main blade section.
If necessary for achieving the desired blade length L, further layers of oxidation-resistant material can be applied to the first intermediate coating 5. The actual abrasive coating 6 is applied either directly to the epitaxial intermediate coating 5 or to the topmost layer of oxidation-resistant material. For this purpose, abrasive particles are mixed together with oxidation-resistant binder material (preferably made of the material used for the intermediate coating(s)) and applied by the LMF method. Here, the abrasive coating 6 does not have to completely cover the intermediate coating 5, but instead can be formed as an individual strip or as a combination of segments of individual strips. In the case of multi-layer abrasive coatings 6, it is advantageous if the proportion of abrasive material 8 increases outward in the radial direction r, because then the outermost coating 6 has the highest proportion of abrasive material 8 and thus the highest resistance to wear.
The following advantages can also be utilized simultaneously for this coating owing to the optimized selection of the binder material:
Low susceptibility to cracking
High resistance to oxidation
Good wetting and encapsulation of the abrasive particles
In terms of production technology, the realization of the abrasive, single-crystal blade tip by the E-LMF method after preceding, conventional coating of the main blade section is particularly interesting: in this process sequence, existing production processes have to be modified only minimally and it is possible to dispense with the masking of the abrasive coating during the application of the MCrAlY protective coatings on the main blade section. The component (turbine blade 1) can therefore be used without carrying out further, subsequent steps immediately after the abrasive blade tip has been applied. It is advantageously possible to dispense with further heat treatment.
One possible production sequence for the production of an abrasive single-crystal turbine blade 1 according to the invention is shown in FIG. 3. An MCrAlY adhesive coating 11 is applied to the surface of a blade body 4, which consists of a single-crystal material, for example a single-crystal Ni-based superalloy, and a ceramic thermal barrier coating (TBC) 12 is applied in turn to said adhesive coating (see FIG. 3 a). The coating on the radially outer blade tip 3, which is in the form of a crown in this exemplary embodiment, is removed mechanically and/or chemically, e.g. ground away, milled away or etched away (see FIG. 3 b), such that the surface of the single-crystal basic body 4 at this point is free from protective coatings, i.e. is uncovered. According to the invention, an epitaxially solidified intermediate coating 5 and an abrasive coating 6 thereon are then applied by E-LMF (see FIG. 3 c).
FIG. 4 shows photographic images of an exemplary realization of such an abrasive single-crystal blade tip 3, which was produced by the LMF method. Here, the blade tip 3 is designed as a crown. The radiation source used was a fiber-coupled high-power diode laser having an output power of 1000 W. The intermediate coating 5 (buffer coating), which is solidified epitaxially and in single-crystal form and is comprised of the alloy known commercially under the name Amdry 995, is firstly arranged on the single-crystal basic body 4 (nickel-based superalloy MK4) on the radially outer surface, the optimum microstructure of said coating also continuing at the interface with the overlying abrasive coating 6 which, in this exemplary embodiment, consists of Amdry 995 as binder material 7 and cBN particles embedded therein as abrasive material 8. Naturally, continuation of the single-crystal microstructure is no longer possible above the first abrasive particles 8.
The following alloys are suitable as the material for the epitaxial intermediate coating 5 or as binder material 7:
    • oxidation-resistant MCrAlY alloys (M═Ni, Co or combinations of both elements) of the γ/γ or γ/γ′ type, the chemical composition of which is selected such that upon epitaxial solidification firstly the γ phase and only then the β or γ′ phase is formed;
    • oxidation-resistant MCrAlY alloys of the γ/β or γ/γ′ type, the chemical composition of which is selected such that it lies in the γ phase region and close to the eutectic boundary line between the γ and β or γ′ phase regions in the ternary Ni—Al—Cr phase diagram or Ni/Co—Al phase diagram;
    • oxidation-resistant MCrAlY alloys of the γ/β or γ/γ′ type having the following chemical composition (amounts in % by weight): 15-30 Cr, 5-10 Al, 0.3-1.2 Y, 0.1-1.2 Si, 0-2 others, remainder Ni, Co;
    • oxidation-resistant MCrAlY alloys of the γ/β type having the following chemical composition (amounts in % by weight): 35-39 Co, 18-24 Cr, 7-9 Al, 0.3-0.8 Y, 0.1-1 Si, 0-2 others, remainder Ni;
    • oxidation-resistant MCrAlY alloys of the γ/γ′ type having the following chemical composition (amounts in % by weight): 18-26 Cr, 5-8 Al, 0.3-1.2 Y, 0.1-1.2 Si, 0-2 others, remainder Ni, Co.
These materials are particularly suitable as intermediate coatings 5, but also as binder material 7 in the abrasive coatings 6. It is advantageous if the material has a solidification interval between the solidus temperature and liquidus temperature ΔT0 of less than 50 K and preferably less than 30 K. This reduces the risk of cracking during solidification.
FIG. 5 shows a coating apparatus 13 for carrying out the method according to the invention and the (epitaxial) LMF process with coaxial injection of the powder particles about a focused, high-intensity laser beam 10. The apparatus 13 is described in detail in U.S. Pat. No. 7,586,061 (B2), the contents of which are incorporated by reference as if fully set forth. Movement of the powder nozzle (or of the workpiece, here turbine blade 1), which is effected with the aid of a robot (not shown), permits full 6-axis flexibility of the process. A dichroic mirror 14 deflects the high-intensity laser light 10 onto the component 1 and focuses it at a small aiming point. The mirror 14 is transparent to the process light, which is coupled to an optical pyrometer (not shown) which makes online control of the temperature of the melt pool 16 possible.
When subjecting the blade tip 3 to laser metal forming, the material 7 for the intermediate coating 5 (or abrasive material 8 and oxidation-resistant binder material 7 for the coating 6) is (are) mixed in a powder nozzle, transported by a carrier gas 15 and then injected concentrically about the laser beam 10 as a focused jet of powder into the melt pool 16 produced by the laser beam 10 on the blade tip 3. In addition, the temperature or temperature distribution in the melt pool is recorded online during the laser metal forming (optical temperature signal 17), and this information is used, with the aid of a control system (not shown), to control the laser power during the laser metal forming and/or to change the relative movement between the laser beam 10 and the turbine blade 1 in a controlled manner.
In the example described, the integrated pyrometer makes it possible to determine the temperature of the melt pool during the laser process. By feedback of the temperature signal 17 to the laser controller (not shown), it is possible with the aid of a real-time control process to adapt the laser power automatically, such that the criteria required for epitaxial solidification are satisfied: to this end, the quotient Gn/Vs has to lie above a material-dependent limit value required for directional, single-crystal solidification. Here, G denotes the local temperature gradient, Vs denotes the speed of the solidification front and n denotes a further material parameter.
The present disclosure provides an inexpensive and simple method for producing abrasive protective coatings for single-crystal turbine blades. The useful service life of the abrasive coating at high operating temperatures is increased by the complete embedding of the abrasive particles in an oxidation-resistant binder matrix. The advantages of abrasive coatings can thus be ensured at least for the duration of the running-in operation.
A good resistance to oxidation is firstly ensured by the special material properties of the binder. Secondly, the solidification properties of the material are optimized for use with epitaxial laser metal forming (E-LMF): the advantageous epitaxial bond to the basic material can thus be achieved while at the same time minimizing the risk of defect formation. Since single-crystal components, e.g. single-crystal turbine blades, are exposed to the greatest thermomechanical loading, the retention of the mechanical integrity (no defects or cracks) is a key prerequisite for use in a turbine.
The abrasive coatings of single-crystal turbine blades have a very high commercial potential in powerful turbines of the most recent generation. Here, single-crystal components are used in the first turbine stage (HPT=high-pressure turbine and/or LPT=low-pressure turbine). At present, there is still no satisfactory solution for optimizing hot gas leakage losses for these components. The present invention makes it possible to reduce the leakage between the heat shield and the tips of the turbine blades. Over the useful service life of the abrasive coating, ovalization of the housing or eccentricity between the rotor and the housing as a result of the turbine blades grinding in can be corrected as part of a suitably configured run-in procedure.
Even after the abrasive coating is lost, the basic body of the blade remains protected throughout the nominal service life owing to the good oxidation resistance of the weld filler used as the binder and buffer coating.
The increased resistance to wear of the abrasive turbine blade with respect to frictional contacts makes it possible to apply relatively dense ceramic coatings to the heat shields. Good rub-in behavior during a run-in procedure can thus be combined with the requisite long-term erosion resistance of the ceramic coatings on the heat shields.
An interesting commercial potential is also the retrofitting or reconditioning of existing blades. These can be modified by the method according to the disclosure in order to achieve reduced leakage losses and thus improved efficiency of the turbine when they are refitted. For this option, it is not necessary to, in advance, remove a protective coating which may already be present on the main blade section. This therefore provides an interesting option for the reconditioning of single-crystal gas turbine blades.
The method can be used with all single-crystal turbine blades 1. The limited service life of the abrasive coating 6, which is dependent on the respective operating conditions (temperature, fuel), must be taken into consideration. The service life is optimized by good distribution and complete embedding of the abrasive particles 8 in the oxidation-resistant binder matrix 7. Nevertheless, the main aim is to protect the turbine blade tip 3 above all during the run-in phase (several dozen to several hundred operating hours). In order to make the best possible use out of the special properties of the abrasive protective coating 6, a run-in procedure tailored to the abrasive turbine blades 1 should be used.
It goes without saying that the invention is not restricted to the exemplary embodiments described.
LIST OF REFERENCE SYMBOLS
    • 1 Turbine blade
    • 2 Rotor
    • 3 Blade tip
    • 4 Single-crystal basic body
    • 5 Epitaxial, oxidation-resistant intermediate coating
    • 6 Wear-resistant and oxidation-resistant coating
    • 7 Binder material
    • 8 Abrasive material
    • 10 Laser beam
    • 11 Metallic protective coating (MCrAlY coating)
    • 12 Ceramic thermal barrier coating (TBC)
    • 13 Coating apparatus
    • 14 Dichroic mirror
    • 15 Carrier gas
    • 16 Melt pool
    • 17 Optical temperature signal
    • r Radial direction
    • L Length of the turbine blade

Claims (18)

What is claimed is:
1. A turbine blade (1) for a turbine rotor (2), the blade (1) having a single-crystal basic body (4) comprising a blade tip (3) and extends in a radial direction (r), at least one oxidation-resistant intermediate coating (5), which is applied by laser metal forming and is epitaxially bonded to the basic body (4), is arranged on a radially outer blade tip (3), and an at least single-layer, wear-resistant and oxidation-resistant coating (6), which is applied by laser metal forming and is comprised of oxidation-resistant binder material (7) and abrasive particles (8) embedded therein, is arranged on at least portions of said epitaxial intermediate coating (5).
2. The turbine blade (1) as claimed in claim 1, wherein the intermediate coating (5) is comprised of an oxidation-resistant γ/β or γ/γ′ type MCrAlY alloy, the chemical composition of which is selected such that upon epitaxial solidification, the γ phase is firstly formed and only then the β or γ′ phase is formed.
3. The turbine blade (1) as claimed in claim 1, wherein the intermediate coating (5) is comprised of an oxidation-resistant MCrAlY alloy having a solidification interval between the solidus temperature and liquidus temperature ΔT0 of less than 50 K, preferably less than 30 K.
4. The turbine blade (1) as claimed in claim 1, wherein the intermediate coating (5) is comprised of an oxidation-resistant γ/β or γ/γ′ type MCrAlY alloy, the chemical composition of which is selected such that it lies in the γ phase region and proximate an eutectic boundary line between the γ and β or γ′ phase regions in a ternary Ni—Al—Cr phase diagram or Ni/Co—Al—Cr phase diagram.
5. The turbine blade (1) as claimed in claim 1, wherein the intermediate coating (5) is comprised of an oxidation-resistant γ/β or γ/γ′ type MCrAlY alloy having the following chemical composition: 15-30% by weight Cr, 5-10% by weight Al, 0.3-1.2% by weight Y, 0.1-1.2% by weight Si, 0-2% by weight others, remainder Ni, Co.
6. The turbine blade (1) as claimed in claim 5, wherein the intermediate coating (5) is comprised of an oxidation-resistant γ/β type MCrAlY alloy having the following chemical composition: 35-39% by weight Co, 18-24% by weight Cr, 7-9% by weight Al, 0.3-0.8% by weight Y, 0.1-1% by weight Si, 0-2% by weight others, remainder Ni.
7. The turbine blade (1) as claimed in claim 5, the intermediate coating (5) is comprised of an oxidation-resistant γ/γ′ type MCrAlY alloy having the following chemical composition: 18-26% by weight Cr, 5-8% by weight Al, 0.3-1.2% by weight Y, 0.1-1.2% by weight Si, 0-2% by weight others, remainder Ni, Co.
8. The turbine blade (1) as claimed in claim 1, wherein the material used for the oxidation-resistant intermediate coating (5) is also used as binder material (7) in the wear-resistant and oxidation-resistant coating (6).
9. The turbine blade (1) as claimed in claim 1, wherein the abrasive material (8) in the wear-resistant and oxidation-resistant coating (6) is cubic boron nitride (cBN).
10. The turbine blade (1) as claimed in claim 1, wherein a proportion of abrasive material (8) in the wear-resistant and oxidation-resistant coating (6), if said coating has a multi-layer form, increases outward in the radial direction (r).
11. The turbine blade (1) as claimed in claim 1, wherein said turbine blade is a reconditioned turbine blade.
12. The turbine blade (1) as claimed in claim 11, wherein the turbine blade was initially used in a preceding service interval without an abrasive blade tip (3).
13. The turbine blade (1) as claimed in claim 1, wherein the turbine blade is a new component.
14. The turbine blade (1) as claimed in claim 1, having a length (L), wherein the length (L) is varied as a function of the number of oxidation-resistant, epitaxial intermediate coatings (5) and/or wear-resistant and oxidation-resistant coatings (6) built up by laser metal forming.
15. A method for producing a turbine blade (1) for a turbine rotor (2), the blade (1) having a single-crystal basic body (4) comprising a blade tip (3) and extends in a radial direction (r), at least one oxidation-resistant intermediate coating (5), which is applied by laser metal forming and is epitaxially bonded to the basic body (4), is arranged on a radially outer blade tip (3), and an at least single-layer, wear-resistant and oxidation-resistant coating (6), which is applied by laser metal forming and is comprised of oxidation-resistant binder material (7) and abrasive particles (8) embedded therein, is arranged on at least portions of said epitaxial intermediate coating (5), the method comprising:
applying, epitaxially, at least one oxidation-resistant intermediate coating (5), by laser metal forming, to the surface of the basic body (4) on the radially outer blade tip (3); and
applying an at least single-layer, wear-resistant and oxidation-resistant coating (6), by laser metal forming, to at least portions of said epitaxial intermediate coating (5).
16. The method as claimed in claim 15, wherein a temperature or temperature distribution in a melt pool (16) is recorded online during build-up of the intermediate coating (5) and of the wear-resistant and oxidation-resistant coating (6) by the laser metal forming method, which is used, with a control system, to control laser power during the laser metal forming method and/or the relative movement between a laser beam (10) and the turbine blade (1) such that quotient Gn/Vs lies above a material-dependent limit value required for directional, single-crystal solidification, where G denotes a local temperature gradient, Vs denotes a speed of the solidification front and n denotes a further material parameter.
17. The method as claimed in claim 16, wherein during the laser metal forming step for producing the wear-resistant and abrasive coating (6), abrasive particles (8) and oxidation-resistant binder material (7) are mixed in a powder nozzle and then injected concentrically about the laser beam (10) as a focused jet of powder into the melt pool (16).
18. The method as claimed in claim 15, wherein, in a preceding production step, at least portions on the surface of the basic body (4) of the turbine blade (1) are coated with an oxidation-resistant, metallic protective coating (11), in particular an MCrAlY coating, and an oxidation-resistant, ceramic thermal barrier coating (12) is optionally applied to said protective coating (11), wherein the at least one metallic and optional ceramic protective coating (11, 12) on the radially outer blade tip (3) is removed by controlled machining, in particular grinding away, CNC milling and/or chemical coating removal, and the epitaxially solidified, oxidation-resistant intermediate coating (5) which is then built up by the laser metal forming is applied such that it at least partially overlaps only with the MCrAlY coating (11) which extends in the radial direction, but not with the additional optional ceramic thermal barrier coating (12).
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EP2317078B2 (en) 2021-09-01
JP2011149419A (en) 2011-08-04
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US20110103967A1 (en) 2011-05-05
JP5757720B2 (en) 2015-07-29

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